94 results about "Airborne system" patented technology

The embodiment of the invention provides a modeling method and device for an airborne system function architecture model, computer equipment and a medium, and relates to the technical field of aviation architecture design, the method comprises the following steps: inputting a design requirement document into an airborne large language model, and in the large language model, under the structural constraint of an airborne system knowledge graph, establishing a design requirement document; the method comprises the following steps: extracting a logical relationship between entities required by airborne system modeling from a design demand document, screening a corresponding airborne meta-model according to the extracted logical relationship between the entities, and constructing a demand graph; constructing and outputting a text model of a concept scene, a text model of a task scene, a text model of a system function, a text model of a logic architecture and a text model of a physical architecture of the airborne system based on the demand graph; and inputting each text model into a system modeling language modeling terminal for visualization to obtain a multi-level functional architecture model of the airborne system. According to the scheme, the modeling efficiency, consistency and normalization are improved.

The invention belongs to the technical field of aviation airborne system design, and provides a helicopter airborne system-oriented novel software architecture and a construction method thereof, and the architecture comprises a hardware abstraction layer, a framework resource layer, an intelligent platform service layer and an application software layer from bottom to top. And the hardware abstraction layer realizes decoupling of hardware and basic software of an operating system. The framework resource layer supports operation of a hybrid key operating system, supports and isolates tasks and application programs with different key levels, software bases and computing power requirements, and provides basic computing communication resources and AI computing power resources. The intelligent platform service layer comprises middleware, a servitization function unit and a servitization management unit, and the servitization function unit comprises atomic services and enhanced services. And the application layer interacts with the intelligent platform service layer and is decoupled from a bottom software and hardware environment. The framework is suitable for unmanned / manned helicopters, and generalization of platform support and maximum reuse of software assets are achieved.

The invention relates to a fault simulation method suitable for engineering simulation of an electric vertical take-off and landing aircraft. The method comprises the following steps: injecting a target fault into a target simulation model of a to-be-tested electric vertical take-off and landing aircraft; controlling a target fault signal to carry out cross-system transmission on a plurality of target airborne systems of the to-be-tested electric vertical take-off and landing aircraft; wherein the target fault signal is a signal triggered based on a target fault; injection data of the target faults and operation data in the cross-system transmission process are obtained so as to be used for evaluating fault responses of the multiple target airborne systems. Through the method and the device, high-fidelity matching of fault injection and an actual fault response scene is realized, and the consistency of fault responses of a plurality of target airborne systems is optimized, so that the authenticity of fault simulation and the effectiveness of fault response evaluation of an electric vertical take-off and landing aircraft jig machine are improved, and the high-fidelity requirement of semi-physical simulation is met.

The invention discloses an aircraft performance monitoring method, device, terminal and system and a storage medium, and the method comprises the steps: obtaining a preprocessed flight data stream from an airborne flight data preprocessing device in the flight process of a target leg, analyzing and processing the flight data meeting the effective leg screening condition in the preprocessed flight data stream to obtain the flight data of the effective leg; based on the flight data of the effective leg, calling an embedded performance factor analysis logic to carry out performance factor analysis so as to obtain a performance factor of the effective leg; and in response to a flight end instruction of the target leg, displaying a performance monitoring result on a display based on the performance factor of each effective leg. According to the invention, while the timeliness of airplane performance monitoring is improved, the interference on airborne system data is avoided, the safety is ensured, and an airplane crew can master the performance condition of an airplane in time.

The invention discloses a high-resolution SAR deception jamming signal rapid generation method and device, and belongs to the technical field of radar countermeasure. The method comprises the following steps: intercepting an SAR signal and measuring parameters of the SAR signal; obtaining a deception jamming template image, and carrying out edge optimization processing; performing two-dimensional partitioning on the template in the distance direction and the azimuth direction to obtain a plurality of sub-templates; calculating a phase compensation function for the central point of each sub-template, and carrying out phase optimization; the optimized sub-templates are superposed, and a high-quality product modulation matrix is generated; and multiplying the matrix by an intercepted SAR signal, and transmitting after digital-to-analog conversion and up-conversion to form a deception jamming signal. According to the method, through block phase compensation and template edge optimization, the imaging quality and concealment of the deception jamming image under the high-resolution SAR are remarkably improved, meanwhile, low calculation complexity is kept, and the method is suitable for satellite-borne and airborne SAR systems.

The application discloses a kind of line segment anti-aliasing parameter optimization method based on objective image quality evaluation under airborne display scene, for line segment anti-aliasing transition width FW Dependence artificial visual debugging, time-consuming, poor consistency, and fixed parameter is difficult to adapt to multi-line width, multi-resolution, arbitrary slope line segment Problem, reference Alpha matrix is generated using SSAA supersampling, PSNR is used as objective quantitative evaluation index to traverse optimization, and optimal FW parameter is obtained automatically and solidified to airborne system.The application can adapt to arbitrary slope and angle line segment rendering, edge smoothing, stable and reliable display effect, small amount of calculation, convenient for hardware implementation, can significantly improve the vector line segment rendering quality and consistency of airborne flat display, helmet display and other scenes, meet the application demand of airborne strong real-time, high reliability.

The invention relates to an avionics system optical fiber communication link health management technology, and provides an airborne communication link fault positioning method and system based on an embedded OFDR, and the method comprises the steps: integrating an embedded OFDR function unit in an airborne network switching module, outputting frequency linear scanning continuous wave test light, and dividing the test light into detection light and reference light; the detection light is sequentially injected into each to-be-detected optical fiber link through the switch exchange matrix, and returned backward Rayleigh scattering light is received and interferes with the reference light to generate a beat frequency signal; a Rayleigh scattering distance map is obtained through analog-to-digital conversion and fast Fourier transform and is compared with a pre-stored health reference map in a differential mode, an abnormal event is recognized, and the position of a fault point is accurately positioned. According to the method, on-line monitoring with sub-millimeter resolution and no blind area can be achieved under the conditions of low power and no communication interruption, multi-link automatic polling, fault link switching and maintenance information reporting are supported, and the requirements for high reliability and BIT autonomous diagnosis of an airborne system are met.

The invention discloses an aircraft airborne system architecture trade-off evaluation method and system based on ADCP, and belongs to the technical field of airborne system evaluation. The method comprises the following steps: selecting an ADCP four-dimensional index; defining primary / secondary index weights by adopting an analytic hierarchy process, and obtaining a comprehensive weight coefficient through consistency check; realizing index normalization transformation through a linear membership function; performing weighted summation to preliminarily screen an optimal framework; calculating physical parameters such as a system capability value and an efficiency value; and verifying whether the optimal architecture meets the condition that at least one core physical parameter is maximum or not, and if not, adjusting the weight or membership function. According to the method, the problems that existing evaluation indexes are disordered, weights are difficult to determine, physical significance is lacked and subjectivity is high are solved, scientificity, accuracy and engineering applicability of evaluation are improved, and the method is suitable for balancing various aircraft airborne system architectures.

The invention provides an airborne system modeling workload quantification method. The airborne system is divided into different levels, modeling workloads are continuously decomposed into modeling workloads of a part layer and modeling workloads of a middle layer (including the modeling workloads between a subsystem layer and a system layer, the modeling workloads between an equipment layer and the subsystem layer and the modeling workloads between the part layer and the equipment layer), and the modeling workloads of the middle layer and the modeling workloads of the part layer and the equipment layer are obtained by subdividing modeling objects. And the purpose of reducing the modeling difficulty is achieved.

The application discloses an airborne control service comprehensive processing system supporting air-ground and air-air cooperative operation, and an airspace multi-state situation comprehensive module combines traffic data, weather data and terrain data with an executing local operation plan or an operation plan to be confirmed for supporting local temporary operation to generate comprehensive situation data; a local temporary control service operation plan generation module establishes an operation plan to be confirmed for supporting local temporary operation considering a potential conflict avoidance space-time region according to judgment on the comprehensive situation data, and outputs the operation plan to a local temporary control service operation plan negotiation module to negotiate with a ground control service system and an airborne system of another aircraft; and the application converts the executing local operation plan or regenerates the operation plan to be confirmed for supporting local temporary operation according to negotiation feedback information. The application can meet the comprehensive service capacity requirement of aircraft operation caused by future change of aviation operation mode.

The invention relates to a lightweight airborne visual tracking method and device based on random projection and a medium, belongs to the technical field of airborne computer vision and target tracking, and can reduce the calculation and storage cost of airborne platform feature processing, guarantee the target tracking precision and adapt to resource limited scenes. According to the invention, lightweight airborne visual tracking is realized based on locality sensitive hash (LSH) random projection, the method is suitable for resource-limited scenes of airborne platforms such as unmanned aerial vehicles and helicopters, and typical challenges such as target scale dramatic change, complex background interference and high-altitude high-angle shooting visual angle offset under airborne vision can be efficiently processed. The core requirements of an airborne system on low computing power occupation, low storage consumption and high real-time performance of a tracking algorithm are met; the LSH random projection technology is organically combined with an existing lightweight tracking architecture, on the premise that tracking precision is not remarkably lost, the calculation and storage cost of feature processing is further reduced, and the method becomes a constraint of breaking through airborne visual tracking resources-performance.

The embodiment of the invention provides a serial port communication filtering method and device based on an FPGA, computer equipment and a medium, and relates to the technical field of control systems.The serial port communication filtering method comprises the steps that serial port communication start bit filtering is carried out based on a first low level counter, a first high level counter and a first time counter; and performing serial port communication data bit, check bit and stop bit filtering based on the second low level counter, the second high level counter and the second time counter. The method comprises the following steps: detecting a falling edge at the beginning of data transmission, performing filtering detection on the falling edge and checking whether the falling edge is an interference signal when detecting that the falling edge exists in a serial port data bit, and receiving serial port communication data and performing filtering operation on a data bit, a check bit and a stop bit according to a filtering algorithm when a non-interference signal is a normal start bit. According to the scheme, the reliability and the stability of serial port communication among products of the airborne system are improved, hardware filtering is reduced, the adaptability of serial port data receiving is enhanced, and the development cost is reduced.

The invention provides a performance testing device for dynamic impact mechanics of an aircraft cockpit airborne system. Comprising a floor, a console support group, a structural member connecting support group, a pedal simulation device, a cockpit console and instrument board, a cockpit seat fixing assembly, a seat assembly, a humanoid test model, a motion data acquisition assembly, a structural horizontal impact test bed and a control computer. The floor is fixed on the structure horizontal impact test bench; the pedal simulation device, the cockpit console and the instrument panel are fixed to the floor through the console support set. The seat assembly is fixed to a floor through the cockpit seat fixing assembly; structural members of the aircraft are fixed to the floor through the structural member connecting support set. The anthropomorphic test model is arranged on the seat assembly, and the motion data acquisition assembly is arranged on the periphery of the anthropomorphic test model. Through the performance testing device, the performance of dynamic impact mechanics of different forms and different types of cockpit airborne systems can be tested.

The invention relates to the field of airplane airborne system design, and discloses a Hypervisor-based cross-system adaptive communication architecture, method and equipment, a virtual machine monitor is introduced between two operating systems, so that the virtual machine monitor is located between the two operating systems, and the virtual machine monitor is responsible for managing hardware resources and providing a virtual operation environment for the two operating systems; according to the method, a virtual machine monitor is partitioned and placed in a shared memory area according to the type of cross-system data, and key real-time data can be preferentially transmitted without waiting for scheduling of a CPU (Central Processing Unit) by performing priority ranking on the data, so that the strict requirement of the aviation field on real-time performance is met; meanwhile, the division of the exclusive channel and the shared channel further optimizes the data transmission path. According to the invention, the data transmission speed can be effectively improved, and the time delay is reduced, so that the communication efficiency in the cross-system service process is improved.

1. Name of the designed product: Airborne communication antenna (5G AeroMACS). 2. Use of the designed product: used for the transmission and reception of radio frequency signals of the airborne 5G AeroMACS system. 3. Design points of the designed product: in shape. 4. Picture or photo best indicating the design points: perspective view.

The invention belongs to the technical field of aviation aircraft design, and particularly relates to a multi-mode power supply dual-redundancy cold standby type liquid cooling airborne system, method and medium, the system comprises liquid cooling pumps, a radiator, a power supply bus bar, time service equipment and a controller, the liquid cooling pumps comprise a liquid cooling pump 1 and a liquid cooling pump 2, inlets of the liquid cooling pump 1 and the liquid cooling pump 2 are connected with liquid cooling electronic equipment, and inlets of the liquid cooling pump 1 and the liquid cooling pump 2 are connected with the controller; outlets of the liquid cooling pump 1 and the liquid cooling pump 2 are connected with the radiator, the radiator is connected with the liquid cooling electronic equipment, the power supply bus bar comprises a power supply bus bar 1 and a power supply bus bar 2, the power supply bus bar 1 supplies power to the liquid cooling pump 1 through the circuit breaker 1, the power supply bus bar 2 supplies power to the liquid cooling pump 2 through the circuit breaker 2, and the power supply bus bar 1 and the power supply bus bar 2 are connected with the controller. The liquid cooling pump 1, the liquid cooling pump 2 and the liquid cooling electronic equipment are all connected with the controller; the time service equipment is connected with the controller; the system self-adaptive capability and task reliability of the dual-redundancy cold standby type environment control liquid cooling system in different power supply modes are improved, the heat dissipation requirement of the liquid cooling electronic equipment in a flight task is guaranteed as much as possible, and the system reliability of an aircraft when the different power supply modes are switched back and forth is guaranteed.

The invention relates to the technical field of airborne system hardware abstraction, and discloses a hardware abstraction method and system for an airborne system, computer equipment and a medium, and the method comprises the steps: abstracting each physical equipment in the airborne system from different types of physical equipment into abstract equipment with the same interface, shielding the physical difference between different types of equipment, and improving the hardware abstraction efficiency. And forming the same abstract device with the same function. And meanwhile, analyzing and counting the interfaces of different types of physical equipment of each type of physical equipment to form a group of uniform interfaces of the abstract equipment. For the upper software, the method shields the physical difference of different hardware of different manufacturers, obviously improves the development efficiency and cross-platform portability of the upper software, and facilitates the development and transplantation of the upper software; for manufacturers, the method unifies the interface requirements of different models of aircrafts, and facilitates formation of lineage design and research and development of products with unified functions and different performances.

The embodiment of the application discloses a power supply configuration architecture of a redundant airborne system, wherein at least four redundant devices are included in the redundant airborne system, a power supply system includes at least two power supply subsystems and professional accumulators, each power supply subsystem has two power supply bus bars, including a main bus bar and an emergency bus bar; the power supply configuration architecture includes: two devices in the power supply configuration architecture are connected with the professional accumulators respectively, one of the two devices is connected with one power supply bus bar in one power supply subsystem, and the other device is connected with one power supply bus bar in the other power supply subsystem; the other two devices are connected with the main bus bar in one power supply subsystem and the emergency bus bar in the other power supply subsystem respectively. The technical scheme provided by the embodiment of the application solves the problem that the existing power supply configuration scheme of the redundant airborne system is difficult to have both the power supply common-mode fault mitigation requirement and the high task reliability level.

The invention provides an airborne system ICD change method and system, and relates to the field of airborne systems.The airborne system ICD change method comprises the following steps that S1, an airborne system ICD change management environment is initialized, and an interface dependency relationship model is established; s2, receiving a change request, analyzing the change request, and identifying a change type; s3, calling the interface dependency relationship model, executing change influence analysis based on the change type, and generating a change influence report; s4, performing change review and implementation based on the change influence report to obtain a change result; and S5, verifying the change result, and generating a change closed-loop report. The problems that in the ICD changing process of an existing airborne system, the flow is not standard, changing analysis is not comprehensive, different types of ICD changing lacks a targeted method, and changing system collaboration is insufficient are solved, the scientific, controllable, efficient and accurate changing method and system are provided, and the compatibility and reliability of the changed system are guaranteed.

The invention relates to the technical field of airborne system design, and discloses an airborne system digital forward design method, device, equipment and medium, a design process from demand analysis, architecture design, architecture tradeoff to simulation verification is established, integration and optimization of the airborne system design process are effectively realized, machine learning and multidisciplinary design optimization are combined, and the design efficiency is improved. According to the method, knowledge in multiple fields such as machinery, electronics and software is fused, design rules are mined from historical design cases through deep learning, a multi-target tradeoff analysis model is established, automatic generation and optimization of an architecture scheme are achieved, dependence on artificial experience is remarkably reduced, airborne system design efficiency is improved, design change cost is reduced, and the method is suitable for large-scale popularization and application. And the reliability of the airborne system is improved.

Grids representing predictions of wind vectors (or velocities) over a ground region are obtained from a model and downscaled to a greater level of resolution based on surface roughness metrics of the ground region. Observations of wind vectors over the ground region are determined from ground-based or airborne systems and assimilated into the grids. Subsequently, grids representing the assimilated wind vectors at an initial time, and the predictions of wind vectors at future times, are provided as inputs to a machine learning model, such as a gradient-boosted decision trees algorithm, along with the surface roughness metrics and other relevant features. A continuous representation of predicted wind vectors over the ground region generated based on outputs received from the model is utilized to make operational decisions regarding an aerial vehicle.

The invention relates to the technical field of airborne system verification, and discloses an airborne system virtual integration verification system and method, through cooperative work of a task scene development assembly, a simulation background engine, an intelligent agent management assembly and a man-machine interaction device, a highly vivid airborne system virtual integration verification environment can be constructed, and the verification efficiency is improved. The requirement conformity of each function performance index of the airborne system digital model in the preset task scene is verified, the design problem can be found in advance through virtual integration verification when the condition for carrying out the physical joint debugging test is not met in the early stage of airborne system design, and the development risk is reduced.

The application discloses a kind of high reliability airborne bus communication device and method, the heterogeneous computing architecture of ARM processor and FPGA processor is used in the bus communication device inside, parallel EMIF and differential serial PCIe double communication are used between ARM processor and FPGA processor, ARM processor is classified according to the ID number of different equipment, and sends to FPGA processor;The data format package of each device is pre-stored in FPGA processor, the received equipment data is compared and verified with format package, after confirming no error, it is sent to system bus simultaneously by bus 1 and bus 2 according to priority level;External equipment passes through the bus communication device through protocol interface, realizes and the bus communication of flight control computer, airborne computer is communicated.The application realizes smooth and reliable communication between airborne equipment and controller system on aircraft, especially manned aircraft, and guarantees the reliable safety of airborne system bus by effective monitoring and management.

The invention belongs to the technical field of aero-engine mechanical system health management, and particularly relates to an aero-engine bearing state monitoring airborne system which comprises a high-frequency vibration acceleration sensor, a lubricating oil metal chip sensor and a comprehensive diagnostor. A vibration conditioning plate and a lubricating oil metal chip conditioning plate are arranged in an engine, and a high-frequency vibration acceleration sensor is connected with the vibration conditioning plate through a rotating speed sensor transmission path; and the lubricating oil metal filing sensor is connected with the lubricating oil metal filing conditioning plate through another rotating speed sensor transmission path. The bearing state monitoring airborne system can monitor the number and quality of metal filing particles passing through a lubricating oil pipeline in real time, can carry out early warning in the early stage of a bearing fault, and draws a trend chart that lubricating oil metal filing is accumulated and increased along with time; the bearing state monitoring airborne system can realize functions of efficiently extracting and analyzing sensitive features such as main bearing fault feature frequency and the like.

The invention provides an Ethernet network card drive multicast-to-unicast realization method, which relates to the field of avionics system airborne networks, and comprises the following steps: configuring a multicast table, obtaining multicast configuration information input by a user, and querying and updating the multicast table according to the multicast configuration information; analyzing the received Ethernet message, acquiring communication address information, judging whether the Ethernet message is a multicast message or not, if so, querying a multicast table, and if a matched multicast group is queried, for each multicast member in the multicast group, sending the multicast message to the multicast table; and modifying the destination multicast group address information of the multicast message into the local unicast address information of the multicast member to generate a unicast message, and transmitting the unicast message to an operating system protocol stack. According to the invention, compatibility of an airborne system Ethernet and a traditional network in application and use modes is realized, smooth transition from the traditional network to the Ethernet is better realized, and the portability of network application is effectively improved.

The invention belongs to the technical field of airborne embedded computers, and provides a processor starting method based on a dual-redundancy Flash storage architecture, and the method comprises the following steps: configuring a main Flash and a standby Flash which are mutually backed up for a processor, and storing the same bootstrap program for the main Flash and the standby Flash; in the starting process of the processor, sensing the starting state of the processor in real time, and judging whether the bootstrap program of the main Flash is abnormal or not according to the starting state; if the SPI chip selection signal is abnormal, dynamically switching the SPI chip selection signal of the processor to the standby Flash by the FPGA, triggering the processor to reset and restarting from the standby Flash; and after the processor is successfully started from the standby Flash, the bootstrap program of the main Flash is automatically repaired. According to the method, an NVRAM is not needed, all SPI interface processors are adapted, the false alarm rate is lower than 0.1%, the system recovery time is smaller than or equal to 2 seconds, and the starting reliability of the airborne system in the severe environment is remarkably improved.

The invention relates to the technical field of airborne system design, and discloses an airborne system model modeling rule making method and device, equipment and a medium, which can deeply fuse airborne system design multi-source heterogeneous knowledge, automatically generate executable modeling rules, improve airborne system design efficiency and model quality, and improve airborne system design efficiency and model quality. The problem that modeling rules are inconsistent due to the fact that traditional modeling rules depend on artificial experience is solved, and standardization, consistency and quality control efficiency of airborne system design are improved.

The embodiment of the invention provides an interface wiring unit for an airborne system, and the interface wiring unit comprises an SoPC chip with a dual-core processor, and the SoPC chip comprises: the dual-core processor in a general processing end processes the receiving and transmitting of data in parallel; the programmable logic end and the universal processing end are interconnected through an AXI bus interface, and a protocol conversion and processing function module in the programmable logic end realizes data conversion and forwarding processing between different interface protocols between a host and external equipment under the control of a dual-core processor; the data conversion and forwarding processing comprises data forwarding between the CAN-FD interfaces and data forwarding between the UART interface and the CAN-FD interface. According to the scheme, redundancy processing of hosts such as a flight control computer, an avionics computer or an electromechanical management computer is separated from communication interface redundancy configuration, so that the flight control computer is prevented from providing various types of physical interface forms, and various communication protocols are adapted.

The invention relates to the technical field of heat storage, in particular to a manufacturing method of a multichannel phase change heat storage unit of an airborne system. The method comprises the following steps: acquiring the thermal load flow of an airborne system; when the thermal load flow is larger than the flow threshold value, the first volume ratio of the cold fluid channel to the phase change heat storage channel is calculated; when the difference between the first volume ratio and 1 is greater than or equal to a proportional threshold, the heat storage unit of the first configuration is manufactured. Therefore, the problem that the temperature of the phase change heat storage unit is easy to change suddenly is solved.